EP0271197B1 - Türanordnung für Flugzeug - Google Patents

Türanordnung für Flugzeug Download PDF

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Publication number
EP0271197B1
EP0271197B1 EP87309595A EP87309595A EP0271197B1 EP 0271197 B1 EP0271197 B1 EP 0271197B1 EP 87309595 A EP87309595 A EP 87309595A EP 87309595 A EP87309595 A EP 87309595A EP 0271197 B1 EP0271197 B1 EP 0271197B1
Authority
EP
European Patent Office
Prior art keywords
door
panel
panels
access opening
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP87309595A
Other languages
English (en)
French (fr)
Other versions
EP0271197A3 (en
EP0271197A2 (de
Inventor
W. Brookes
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
Original Assignee
British Aerospace PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from GB868626125A external-priority patent/GB8626125D0/en
Priority claimed from GB868627089A external-priority patent/GB8627089D0/en
Application filed by British Aerospace PLC filed Critical British Aerospace PLC
Publication of EP0271197A2 publication Critical patent/EP0271197A2/de
Publication of EP0271197A3 publication Critical patent/EP0271197A3/en
Application granted granted Critical
Publication of EP0271197B1 publication Critical patent/EP0271197B1/de
Expired legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1407—Doors; surrounding frames
    • B64C1/1415—Cargo doors, e.g. incorporating ramps

Definitions

  • This invention relates to door arrangements for aircraft. More particularly it is concerned with an improved rear loading door arrangement, typically for use in transport aircraft.
  • Rear loading door arrangements are well known in connection with in-flight delivery of payloads and these door arrangements may be determined by a given payload envelope which they must accommodate; that is they must be capable of giving adequate clearance to enable the payload to pass into and out of the aircraft.
  • the rear fuselage shape may be determined by these loading requirements and since the doors will conform to the fuselage shape, in the case of outwardly opening doors their use in the airborne payload delivery mode will necessitate the doors protruding into the airstream which is aerodynamically undesirable. This may be overcome by the use of an inwardly opening door but the intrusion on the contained volume of the fuselage will again determine the rear fuselage shape if the required payload envelope and the locus of travel into or out of the aircraft is to be accommodated. It is the object of the present invention to provide an improved rear loading door arrangement.
  • US Patent 3 424 411 discloses a door arrangement for aircraft including an access opening in the fuselage of the aircraft and a multiple panel door assembly associated with the access opening, the door panel assembly being adaptably configured such that in its closed position it generally conforms to the aircraft fuselage profile to close off the access opening and in its open position it adopts a folded configuration.
  • the door assembly comprises a series of adjacent door panel positions each hingeably located to its adjacent panel or panels such that, in combination, the panels effectively form a single door panel assembly.
  • the arrangement includes actuating means for drawing the door assembly from the access opening and stowing it in folded open configuration.
  • the multiple door arrangement included a centre panel and upper panels hingeably located to each inner longitudinal edge of the centre panel.
  • the outer edges of the upper panels incorporated latches for securing the door assembly, when closed, to the structural surround of the access opening. These latches however, do not function as hinges since they have no pivotal connection for that purpose. Indeed the arrangement requires that prior to the multiple door assembly being drawn from its access opening the upper panels are swung upwardly by actuating means to fold concurrently on to the centre panel. This action occurs quite distinctly prior to withdrawing the door assembly from the access opening.
  • a door arrangement for aircraft including an access opening in the fuselage of said aircraft, a multiple panel door assembly associated with said access opening and actuating means for moving said door assembly with respect to said access opening, said door assembly being adaptably configured and comprising a series of adjacent door panel portions each hingeably located to its adjacent panel or panels such that, in combination, the panels effectively form a single door panel assembly, the arrangement being such that, in its closed position said door assembly substantially conforms to the aircraft fuselage profile to close off said access opening and in its open position it adapts a folded configuration, characterised in that said door panel assembly as a whole is hingedly attached substantially at its longitudinal boundaries to fuselage structure such than, when unfolded, it forms a substantially closed contour with said fuselage structure.
  • Figure 1 illustrates a side elevation on a rearward portion of a transport aircraft configured for the freight carrying role.
  • Figure 2 illustrates an inverted plan on the rearward portion of the same transport aircraft viewed in direction of Arrow II in Figure 1.
  • Figure 3 is an end view on the same rearward portion viewed in direction of Arrow III in Figure 1.
  • Figure 4 is a diagrammatic vertical cross-section through the fuselage illustrating one embodiment of a door arrangement in accordance with the invention.
  • FIGS 5A - 5C inclusive illustrate, diagrammatically, three stages in the door opening sequence in accordance with the present invention.
  • Figure 6 illustrates a typical hinged interconnection between adjacent door panel portions, indicated as Detail VI in Figure 5A.
  • FIGS 7A - 7C inclusive illustrates diagrammatically three stages in the door opening sequence of an alternative embodiment in accordance with the present invention.
  • Figure 8 is a diagrammatic vertical cross-section through the fuselage illustrating an alternative embodiment of a door arrangement in accordance with the invention.
  • Figures 9 and 10 illustrate one embodiment of door actuating mechanism.
  • Figures 11 and 12 illustrate an alternative embodiment of door actuating mechanism.
  • Figure 1 and Figure 2 illustrate a rearward portion of a transport aircraft 10 comprising a rear fuselage portion 11 and a tail fin 12.
  • the rear fuselage portion 11, sharply tapering in a rearwards direction includes a retractable loading ramp 13, air brakes 19 and a rear-loading door arrangement 20, the subject of the present invention.
  • the loading ramp 13 is shown in retracted position 13a where it conforms to the fuselage profile 14 and a deployed position 13b. It is pivotally located to the fuselage structure by means not shown but arranged such that the inner ramp surface 16 substantially intersects the aircraft floor 17 to enable transfer of freight and other loads into and out of the aircraft.
  • a supplementary ramp 18 extends between the deployed ramp door 13b and the ground 15.
  • Figure 2 is composite illustration, showing at the upper half (as illustrated) relative to the aircraft longitudinal centre line 21, the ramp door 13, air brake 19 and rear-loading door 20 in open position and the lower half the same components in closed configuration.
  • the ramp 13 is a single component symmetrically disposed about the aircraft longitudinal centre line 21.
  • the rear loading door arrangement 20 will now be described in detail. Although associated with a fuselage of circular cross-sectional form in the present embodiment it is equally applicable to non-circular arrangements.
  • the arrangement comprises a series of five interconnected door panel portions hingedly depending from the rear fuselage fixed structure 22 and configured such that when closed, in combination they conform to the aerodynamic profile of the rear fuselage.
  • the longitudinal boundary of each door panel portion is determined by the radial disposition of longitudinal hinge axes as illustrated in Figure 4 and which are symmetrically disposed to port and starboard sides of the aircraft, namely, upper hinge axes 23, which additionally determines the lower boundary of the fuselage fixed structure 22, intermediate hinge axes 24 and lower hinge axes 25.
  • each panel is interconnected to its adjacent panel by hinge 30.
  • the hinge is shown located adjacent the inner surface 31 of the door panels 27 and 28 with a longitudinal flexible seal 32 located to the end face 33 of door panel 28 close to the door outer surface. This is by way of example only; a similar arrangement is applicable at the interconnections between door panels 28 and 29 and between door panel 27 and the fixed structure 22.
  • the lower panel portion 29 includes a horizontal inner face 34 providing a mounting face for the door actuating mechanism not illustrated in this diagrammatic section but described hereafter with references to Figures 9 - 12 inclusive.
  • FIGS 9 and 10 describe one embodiment of door actuating mechanism and for reasons of clarity the outline of the aircraft is shown in chain dot.
  • the lower door panel 29 is shown in full line in the door closed position and in chain dot line 29a in the open position and the actuating mechanism is configured to give an effective pivotal rotation of the door about a theoretical transverse door hinge axis 35.
  • the remaining interconnected door panel are omitted for reasons of clarity.
  • Transversely spaced apart attachment brackets 36 and 37 provide pivotal attachments 38 and 39 respectively to the door actuating assembly 40.
  • This assembly comprises a forward diagonally disposed lever beam 41 and a rearward diagonally disposed lever beam 42 respectively including upper pivotal attachments 43 and 44 respectively to the fixed fuselage structure 22 and lower pivotal attachments 45 and 46 to links 47 and 48 providing interconnection between the lever beams 41 and 42 and the door panel 29.
  • the lever beam 41 further includes a bell crank portion 49 incorporating a pivotal attachment 51 to an hydraulic jack 52 pivotally attached to the fixed fuselage structure 22 and a pivotal attachment 53 to a push rod 54 pivotally attached at its rearward extremity 55 to a bell crank portion 56 extending upwardly from lever beam 42.
  • operation of the hydraulic jack 52 effects rotation of the door panel 29 from its closed position to the stowed position 29a.
  • Figures 11 and 12 illustrate one further embodiment of actuating mechanism in which the lower panel portion is pivotally located to the fixed fuselage structure 22 at its rearward extremity about a transverse hinge axis 57 and, as in the previously described embodiment is movable from its closed position to its deployed position 29a as indicated in chain-dot-line.
  • the mechanism 58 for effecting such actuation comprises a yoke member 59 including upper pivotal attachments 60 to hinge brackets 61 mounted upon the rearward face of a diagonally disposed structural member 62 and lower pivotal attachments 63 to a pair of links 64 providing interconnection to attachments brackets 65 mounted upon the door inner surface 34.
  • Twin hydraulic jacks 66 are pivotally located at 67 to the structural member 62 and have a pivotal attachment 68. Actuation of the hydraulic jacks 67 causes angular displacement of the yoke 59 to effect door opening.
  • the yoke is configured so that when the door is open it will in no way obstruct the transfer of loads into and out of the aircraft and additionally it will straddle the door assembly when in its fully stowed position.
  • the door opening sequence is diagrammatically illustrated in Figures 5A - 5C inclusive.
  • a 'clamshell effect' closure of the associated door panel 27 and 28 is automatically induced, with differential hinging movement between the adjacent panels and the whole hinging about the fixed fuselage structure 22 into a compact stowed configuration.
  • the upper door panel 27 is hingeably located to the fixed structure 22 and moves about the longitudinal hinge axis 23.
  • Figure 8 An alternative embodiment will now be described with reference to Figures 7A - 7C inclusive and Figure 8 which provides variation in the closure geometry and improved headroom. Where relevant similar reference numbers are used for components comparable with the previous embodiment.
  • the section of Figure 8 represents a typical door hinge station and there will be at least two such stations along the length of the loading door.
  • the rear loading door arrangement comprises a series of five interconnected door panel portions, upper and intermediate door panels 27 and 28 (port and starboard) and a single lower door panel 29.
  • the longitudinal boundaries of each panel is determined by radial disposition of longitudinal hinge axes.
  • the upper longitudinal boundary of the upper door panel 27 does not constitute a hinge axis. Hinging and sealing of the interconnected door panel portions is as previously discussed with reference to Figure 6.
  • the upper door panels 27 each include cranked cantilever beams 71 extending upwardly and inwardly to support a 4-bar linkage geometric arrangement.
  • the upper region of the beams 71 includes a pivotal attachment 76 to a lower link 72 and a pivotal attachment 77 to an upper link 73 these links respectively including outer pivotal attachments 75 and 74 to the fixed fuselage structural member 70.
  • the links are convergently arranged such that the theoretical intersection of the longitudinal centre lines passing through the respective pivot centre lines constitutes an instantaneous virtual hinge point 69 external to the fuselage profile.
  • the unique composite construction and operating geometry of the rear loading door of the present invention offers significant aerodynamic and operational benefit particularly in the in-flight delivery mode and reduces to a significant degree the limitations associated with prior art loading door arrangements.
  • the present door arrangement may be used in conjunction with a loading ramp or in particular rear fuselage arrangements may be utilised alone. Variations can be applied to meet specific requirements.
  • airbrakes 19 are positioned such that they can act as doors, reducing the size needed for the rear loading doors. When the rear loading doors are opened, the air brakes are opened just sufficiently to clear the path of the payload but not such as would produce high aerodynamic drag in the in-flight mode.
  • a further advantage of this arrangement is that whilst the rear loading doors in their open configuration lie substantially within the main envelope of the fuselage and thus well clear of the main airstream, partly deployed airbrakes shroud those parts of the assembly lying outside the main envelope from the full force of the airstream. This is illustrated in Figure 2, the lower half of the view showing airbrake 19 and the loading doors in closed position, the upper half of the view showing the partially opened air brake shielding the deployed loading door.
  • the multiple panel assembly may retain the upper panels 27 hingeably located at or about the longitudinal boundaries of the access opening but with the lower panel 29 replaced with a pair of panels hingeably located to each other along the bottom longitudinal centre line and at their upper boundaries to the upper panels 27 or to intermediate panels 28, for example.
  • the actuating means would, when operated, cause the assembly to fold upwards about the lower hinge centre.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Hinges (AREA)
  • Extensible Doors And Revolving Doors (AREA)

Claims (8)

  1. Türanordnung für ein Flugzeug mit einer Zugangsöffnung im Rumpf (11) des Flugzeuges, mit einem aus mehreren Platten bestehenden Türaufbau (20), der der Zugangsöffnung zugeordnet ist und mit einem Antrieb (40) um den Türaufbau gegenüber der Zugangsöffnung zu bewegen, wobei der Türaufbau anpassungsfähig gestaltet ist und eine Reihe von Türplattenabschnitten (27, 28, 29) aufweist, die jeweils an ihrer benachbarten Platte oder an benachbarten Platten so angelenkt sind, daß die Platten zusammen wirksam einen einzigen Türplattenaufbau bilden, wobei die Anordnung derart getroffen ist, daß in Schließstellung der Türaufbau (20) im wesentlichen mit dem Profil des Flugzeugrumpfes übereinstimmt, um die Eingangsöffnung zu schließen während in der Öffnungsstellung der Türaufbau eine Faltkonfiguration einnimmt, dadurch gekennzeichnet, daß der Türplattenaufbau (20) als Ganzes schwenkbar im wesentlichen an seinen Längsbegrenzungen am Rumpfaufbau (22) derart angelenkt ist, daß in entfalteter Stellung eine im wesentlichen geschlossene Kontur mit dem Rumpfaufbau geschaffen wird.
  2. Türanordung nach Anspruch 1, bei welchem das Flugzeug (10) als Frachttransporter ausgebildet ist und einen hinteren Rumpfabschnitt (11) mit einem sich nach hinten erstreckenden oberen strukturellen Teil (22) über der Längsmittellinie hat, um Backbord- und Steuerbord-Längsbegrenzungen (23) der Zugangsöffnung zu definieren, wobei der Mehrfach-Plattentüraufbau (20) von der Backbord- und der Steuerbordseite des oberen strukturellen Aufbaus (22) derart herabhängt, daß in Schließstellung eine Anpassung und Definition der rückwärtigen Rumpfgestalt (14) unter dem festen oberen Aufbau erfolgt, daß jedoch dann, wenn der Aufbau aus der Schließstellung durch den Antrieb (40) weggezogen wird, dieser in gefalteter Offenstellung benachbart zu dem oberen strukturellen Aufbau (22) verstaut wird.
  3. Türanordnung nach den Ansprüchen 1 oder 2, bei welcher die Längsbegrenzungen des Türaufbaus (20) im wesentlich benachbart zu den Backbord- und den Steuerbord-Längsbegrenzungen der Zugangsöffnung liegen und die Grenzen der benachbarten Türplattenanordnungen (27) durch die in Längsrichtung verlaufenden Gelenkachsen definiert sind und benachbart dazu liegen.
  4. Türanordnung nach Anspruch 2, bei welchem die Mehrfachplattentüraufbauten (20) eine untere Platte (29) aufweisen, die symmetrisch um die Flugzeuglängsmittellinie (21) angeordnet sind, wobei obere Platten (27) im wesentlichen an den Längsbegrenzungen der Zugangsöffnung schwenkbar (30) angelenkt sind und wenigstens eine Zwischenplatte (28) schwenkbar die oberen mit den unteren Platten verbindet.
  5. Türanordnung nach Anspruch 4, bei welcher die oberen Platten (27) schwenkbar (30) an ihren oberen Längsrändern mit den Längsbegrenzungen der Zugangsöffnung verbunden sind.
  6. Türanordnung nach Anspruch 4, bei welchem der Mehrfachplattentüraufbau (20) schwenkbar von dem festen oberen Aufbau (22) durch eine geometrische Viergelenkanordnung (71-76) verbunden ist, wobei die Anordnung einen Auslegerarm (71) aufweist, der auf den oberen Platten (27) gelagert ist und sich nach oben und innen allgemein diagonal erstreckt, wobei der Auslegerarm jeweils eine erste Schwenkbefestigung (76) mit einem ersten unteren Lenker (72) und eine zweite Schwenkbefestigung (77) mit einem zweiten oberen Lenker (73) aufweist, wobei der erste und zweite Lenker jeweils dritte (75) und vierte (74) Schwenkbefestigungen mit dem festen oberen Aufbau (70) aufweisen und erster (72) und zweiter (73) Lenker konvergierend derart angeordnet sind, daß der theoretische Schnittpunkt der Längsmittellinien durch die jeweiligen Schwenkzentren hindurchläuft, die die einen augenblicklichen virtuellen Schwenkpunkt(69)außerhalb des Rumpfprofiles bilden.
  7. Türanordnung nach den Ansprüchen 2 oder 4, bei welchem die untere Platte (29) schwenkbar (57) an dem ersten oberen strukturellen Abschnitt (22) am rückwärtigen Ende angelenkt ist und die Betätigungseinrichtung (40), die an der unteren Platte (29) angreift, eine Winkelversetzung dieser Platte und eine zugeordnete Faltung der oberen (27) und mittleren (28) Plattenabschnitte von der vollen Schließstellung in die Verstaustellung bewirkt.
  8. Türanordnung nach Anspruch 2, bei welcher der Mehrfachplattentüraufbau (20) obere Platten (27) aufweist, die schwenkbar im wesentlichen an ihren jeweiligen Backbord-und Steuerbord-Längsbegrenzungen der Zugangsöffnung angelenkt sind, und untere Platten (29) an den Backbord- und Steuerbordseiten der Längsmittellinie (21) der Zugangsöffnung liegen und schwenkbar miteinander um die Längsmittellinie (21) angelenkt sind, wobei jede Platte schwenkbar im wesentlichen an ihren jeweiligen Seitenrändern der oberen Platten (27) oder an den mittleren Platten (28) angeordnet ist und die oberen und unteren Platten verbindet.
EP87309595A 1986-10-31 1987-10-29 Türanordnung für Flugzeug Expired EP0271197B1 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
GB8626125 1986-10-31
GB868626125A GB8626125D0 (en) 1986-10-31 1986-10-31 Door arrangement for aircraft
GB868627089A GB8627089D0 (en) 1986-11-12 1986-11-12 Door arrangements for aircraft
GB8627089 1986-11-12

Publications (3)

Publication Number Publication Date
EP0271197A2 EP0271197A2 (de) 1988-06-15
EP0271197A3 EP0271197A3 (en) 1988-07-06
EP0271197B1 true EP0271197B1 (de) 1991-02-27

Family

ID=26291480

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87309595A Expired EP0271197B1 (de) 1986-10-31 1987-10-29 Türanordnung für Flugzeug

Country Status (4)

Country Link
US (1) US4832286A (de)
EP (1) EP0271197B1 (de)
DE (1) DE3768219D1 (de)
ES (1) ES2021059B3 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5241722A (en) * 1991-01-31 1993-09-07 Mcdonnell Douglas Corporation Ramp system
US6382562B1 (en) 1999-11-10 2002-05-07 The Boeing Company AFT egress and control device for an aircraft
US7108228B1 (en) * 2005-02-02 2006-09-19 Manfred Marshall Hydrogen-fueled spacecraft
EP3050794B1 (de) * 2015-01-28 2017-05-10 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Flugzeug mit nach innen faltbarer hecktür
GB2620637A (en) * 2022-07-15 2024-01-17 Gkn Aerospace Services Ltd Electric vertical take-off and landing vehicle

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3128068A (en) * 1962-11-09 1964-04-07 Lockheed Aircraft Corp Petal type door for cargo aircraft
DE1182963B (de) * 1963-08-01 1964-12-03 Ernst Heinkel Flugzeugbau G M Einziehbare Fahrwerkeinrichtung fuer ein Transportflugzeug, insbesondere einen Senkrechtstarter
US3424411A (en) * 1967-08-22 1969-01-28 Lockheed Aircraft Corp Door assembly for cargo aircraft
US3730456A (en) * 1970-04-14 1973-05-01 Hawker Siddeley Aviation Ltd Aircraft with lift engines
GB1347690A (en) * 1970-10-10 1974-02-27 British Aircraft Corp Ltd Doors
US4097009A (en) * 1977-04-27 1978-06-27 The Boeing Company Aircraft ramp door
US4140291A (en) * 1977-10-13 1979-02-20 The United States Of America As Represented By The Secretary Of The Air Force Ramp toe stowage system
US4167258A (en) * 1978-03-24 1979-09-11 Lockheed Corporation Aft cargo door for aircraft

Also Published As

Publication number Publication date
DE3768219D1 (de) 1991-04-04
EP0271197A3 (en) 1988-07-06
EP0271197A2 (de) 1988-06-15
US4832286A (en) 1989-05-23
ES2021059B3 (es) 1991-10-16

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